Formation algorithms of sequential control for spacecraft rendezvous with low-thrust

The problem of control program formation during orbital rendezvous maneuver at low Earth orbits is studied. Rendezvous of two spacecraft are considered. The first is an active spacecraft, equipped with low-trust engines and, the second, is passive spacecraft. Using the linearized equations of motion, the secular and periodic components of relative motion are explicitly allocated. The control program is a consistent correction of the relative motion parameters to the specified values with transversal and binormal trust direction. During formation of the control program, the analytical solutions and the iterative procedure are used. The numerical simulation of rendezvous maneuver is carried out.